XFOIL Version 6.94 Calculated polar for: S4053 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4030 0.00740 0.00248 -0.0851 0.7895 1.0000 0.500 0.4507 0.00755 0.00247 -0.0833 0.7702 1.0000 1.000 0.4992 0.00771 0.00250 -0.0816 0.7507 1.0000 1.500 0.5483 0.00788 0.00256 -0.0800 0.7315 1.0000 2.000 0.5977 0.00807 0.00265 -0.0785 0.7117 1.0000 2.500 0.6468 0.00826 0.00277 -0.0768 0.6903 1.0000 3.000 0.6959 0.00843 0.00292 -0.0752 0.6668 1.0000 3.500 0.7448 0.00863 0.00310 -0.0735 0.6400 1.0000 4.000 0.7930 0.00883 0.00327 -0.0717 0.6074 1.0000 4.500 0.8404 0.00910 0.00353 -0.0698 0.5678 1.0000 5.000 0.8859 0.00950 0.00382 -0.0675 0.5132 1.0000 5.500 0.9268 0.01025 0.00426 -0.0646 0.4294 1.0000 6.000 0.9648 0.01135 0.00497 -0.0615 0.3353 1.0000 6.500 1.0010 0.01270 0.00596 -0.0583 0.2431 1.0000 7.000 1.0354 0.01428 0.00712 -0.0551 0.1560 1.0000 7.500 1.0689 0.01594 0.00851 -0.0516 0.1003 1.0000 8.000 1.1010 0.01764 0.01017 -0.0479 0.0741 1.0000 8.500 1.1355 0.01902 0.01160 -0.0448 0.0575 1.0000 9.000 1.1640 0.02074 0.01342 -0.0407 0.0467 1.0000 9.500 1.1812 0.02299 0.01576 -0.0350 0.0365 1.0000 10.000 1.2063 0.02460 0.01757 -0.0308 0.0276 1.0000 10.500 1.2195 0.02764 0.02085 -0.0255 0.0226 1.0000 11.000 1.2363 0.03040 0.02384 -0.0213 0.0194 1.0000 11.500 1.2429 0.03517 0.02888 -0.0170 0.0171 1.0000 12.000 1.2506 0.03971 0.03386 -0.0134 0.0157 1.0000 12.500 1.2555 0.04388 0.03839 -0.0108 0.0142 1.0000 13.000 1.2482 0.05010 0.04505 -0.0087 0.0134 1.0000 13.500 1.2328 0.05753 0.05291 -0.0082 0.0131 1.0000 14.000 1.2112 0.06625 0.06201 -0.0097 0.0126 1.0000 14.500 1.1782 0.07790 0.07409 -0.0139 0.0125 1.0000 15.000 1.1345 0.09352 0.09015 -0.0219 0.0128 1.0000 15.500 1.0768 0.11553 0.11259 -0.0355 0.0136 1.0000 16.000 0.9819 0.15416 0.15149 -0.0586 0.0158 1.0000 16.500 0.9259 0.19070 0.18783 -0.0748 0.0210 1.0000 17.000 0.7430 0.18766 0.18531 -0.0750 0.0359 1.0000 17.500 0.7394 0.19658 0.19423 -0.0819 0.0315 1.0000 18.000 0.7505 0.20297 0.20065 -0.0848 0.0276 1.0000 18.500 0.7661 0.21038 0.20810 -0.0861 0.0256 1.0000 20.000 0.7782 0.23801 0.23574 -0.1001 0.0241 1.0000 20.500 0.7850 0.24639 0.24416 -0.1045 0.0214 1.0000 21.000 0.7950 0.25367 0.25147 -0.1077 0.0184 1.0000 21.500 0.8076 0.26079 0.25863 -0.1099 0.0172 1.0000 22.000 0.8175 0.27249 0.27033 -0.1127 0.0166 1.0000 22.500 0.8214 0.28100 0.27885 -0.1173 0.0163 1.0000 23.000 0.8266 0.28928 0.28715 -0.1220 0.0158 1.0000 23.500 0.8341 0.29825 0.29614 -0.1258 0.0142 1.0000 24.000 0.8420 0.30701 0.30493 -0.1293 0.0128 1.0000 24.500 0.8500 0.31556 0.31350 -0.1326 0.0120 1.0000 25.000 0.8583 0.32371 0.32170 -0.1356 0.0111 1.0000 26.000 0.8754 0.34432 0.34237 -0.1411 0.0105 1.0000 26.500 0.8797 0.35349 0.35155 -0.1452 0.0104 1.0000 27.000 0.8843 0.36243 0.36051 -0.1492 0.0103 1.0000 27.500 0.8904 0.37193 0.37004 -0.1531 0.0089 1.0000 28.000 0.8964 0.38152 0.37965 -0.1564 0.0078 1.0000 28.500 0.9021 0.39085 0.38902 -0.1597 0.0074 1.0000 29.000 0.9074 0.39975 0.39797 -0.1628 0.0068 1.0000 29.500 0.9124 0.40886 0.40711 -0.1659 0.0067 1.0000 30.000 0.9180 0.42080 0.41907 -0.1685 0.0064 1.0000 30.500 0.9217 0.43019 0.42848 -0.1718 0.0064 1.0000 31.000 0.9249 0.44014 0.43845 -0.1755 0.0063 1.0000 31.500 0.9286 0.44994 0.44827 -0.1789 0.0062 1.0000 32.000 0.9327 0.46040 0.45876 -0.1821 0.0056 1.0000 32.500 0.9360 0.47021 0.46862 -0.1852 0.0047 1.0000